Abstract: A intermediate range/short range laser defense system (10) for use against chemical and biological submunitions (36). The system includes a source (12) of a high power laser beam (14) which is directed by a beam steering device (16). The beam steering device (16) is controlled by a processor (20) which generates control signals (22) for orienting the beam steering device (16) to the control the laser beam (18). The processor (20) operates in a LACROSST mode which enables detection of the submunitions (36). The processor (20) receives tracking information from a detector (26) and tracker (24). The processor directs the laser beam (18) towards a centroid (40) of a dispersion pattern or cloud (38). The laser beam (18) is then directed in an outward, spiral path (42) from centroid (40). When the laser beam (18) encounters a submunition (36), the laser beam locks onto the submunition (36) in order to heat the submunition (36), thereby denaturing or destroying the submunition (36).

Abstract: A land mine arming/disarming system is provided in which a satellite or other airborne vehicle may remotely arm and/or disarm land mines via signals transmitted through atmospheric free space. In such a manner, land mines are less of a health hazard when conflict situations are not present.

Abstract: A defense missile system for an aircraft to provide protection against hostile attack on the aircraft, the system including an aerodynamically shaped launch housing structured for external mounting on the aircraft, and a missile assembly fitted within an interior launch chamber of the launch housing. The missile assembly includes at least one, and preferably several infrared guided missiles each contained within an elongate tube and having a propulsion engine at one end and a seeker head at the opposite end. A missile support structure holds each of the missiles within the launch chamber such that the missile seeker heads are at least partially exposed through an open aft end of the launch housing. A cylinder containing pressurized coolant gas is supported within the launch chamber and is interconnected to each of the missiles for providing coolant gas to the respective seeker heads.

Abstract: Selected rows of seats for a wide body aircraft (i.e., having two or more passenger aisles) have seat groups that can expand or contract to change the number of seats in a row and the seat width. Conversion is possible with all seat components remaining attached to their respective frames, so that no detachable units have to be stowed. The convertible seat configurations are adaptable to incorporating individual amenities, including individual electronic displays.

Abstract: An aircraft system intended for gliders and low power-to-weight aircraft, to aid the pilot in locating updrafts associated with the buoyancy of humid air in the convective layer of the atmosphere, namely moist thermals. The system comprises a pair of laterally spaced hygrometers, generally at the wingtips. Four types of hygrometer units are described; resistive, piezoelectric, spectrometric, and capacitive. Humidity data is transmitted to the cockpit by telemetry links, of which four types are also described; by dedicated wiring, by carrier current using wingtip position lights wiring, by modulated infrared beams, and by low-power radio waves. The system monitors the difference of humidity between left and right sensors, and also the rate of change of humidity of one or both sensors as a function of time.

Abstract: A variable flow-restricting and apportioning device for an aircraft ejector rack system having a pair of fluid-actuated thrusters includes a pair of rotatable feed conduits for supplying pressurized fluid to the thrusters. Each feed conduit has an exit flow passage at its exit end which is eccentric relative to the longitudinal axis about which the conduit is rotatable, and the exit end of each feed conduit slidably fits into a female receptacle in a receiver in fluid communication with one of the thrusters. Each receptacle includes a mating face therein which has a receiver port for supplying fluid to the respective thruster. The receiver port is eccentric relative to the rotational axis of the feed conduit. Rotating each feed conduit relative to the respective receiver causes varying degree of overlap between the eccentric exit flow passages and the eccentric receiver ports, thereby defining variable-size flow orifices at each receiver.

Abstract: A vehicle hydropneumatic suspension comprising four double acting rams (1, 2, 3, 4) each between respective one of four spaced wheels at comers of the vehicle. First conduits (9, 11) connecting main chambers (1a, 2a) of front rams (1, 2) with diagonally opposite rear cylinder minor chambers (3b, 4b), respectively, and, second conduits (10, 12) connecting minor chambers (1b, 2b) with main chambers of diagonally opposite rams (3a, 4a), respectively. A load distribution unit (13) has two cylindrical chambers (13a, 13b) each separated by a piston into. respectively, chambers (14, 15) and (16, 17). Conduits (9a, 10a, 11a, 12a) connect respectively conduits (9, 10, 11, 12) to chambers (14, 16, 17, 15). The pistons are connected by a resilient means (20) to allow relative piston movement to provide for independent control of pitch and roll of the vehicle.

Abstract: An internal combustion catapult for loads such as an aircraft using much of the conventional steam system in that an existing elongated launch tube is utilized with an existing movable piston. The steam generation system may be replaced and a plurality of combustors positioned at the aft end of the launch tube facing the trailing end of the piston. Each of these combustors includes an injector assembly for supplying a combustible propellant. At least one igniter is operatively positioned with respect to the combustor to ignite the combustible propellant to form hot launch gases at high pressure to project the piston down the launch tube to launch the aircraft. A water manifold injects water into the combustion gases to cool them and form steam to propel the piston down the launch tube.

Abstract: A missile for detecting and combatting enemy helicopters has an infrared homing head with an infrared lens and infrared sensor that will emit electrical signals, depending on incident infrared radiation, and the sensor is designed as a two-dimensional detector matrix consisting of a number of punctiform detector cells arranged essentially in the focal plane of the infrared lens. The homing head includes an arrangement for acquiring a target and determining the type of target from the target information by individually scanning each of the detector cells quickly one after another by evaluating the amplitude and frequency of the electrical signals. The determination includes determining the relative position of the target to the optical axis of the homing head and the homing head will then steer the missile to hit the target.

Abstract: In a non-electric system for initiating explosives, a shock tube is initiated by the detonation of a low-energy detonating cord (LEDC) whose wall has been placed adjacent to an initiation-sensitive region of a thin membrane in the shock tube, or in a capping member to an open end of a shock tube or in a capping member to the detonator itself, wherein the inner surface of the bore of the shock tube or the end-capping member is coated with a reactive composition of an explosive or a deflagrating compound. The end capping member fits over and seals the open end of the shock tube or fits in and seals a detonator with or without a shock tube in it, acting as a shock tube itself. The thin membrane accepts the detonation from the LEDC, whereby the shock tube or capping member is initiated and relays a pressure pulse to the shock tube or the detonator affixed thereto. Novel shock tubes, shock tube/detonator units, and a detonator for use in the hybrid shock tube/LEDC system are disclosed.

Abstract: A radar highway motor vehicle guidance apparatus for guiding a land vehicle along a roadway using a backward looking and a forward looking, lateral position sensing, monopulse tracking radar guidance apparatus which transmits radar pulses backward and forward of the vehicle. The pulses are reflected back to the vehicle by a stripe distributed along the roadway. The stripe is a frequency selective surface which generates retro-reflective grating lobes at an operating frequency of the tracking radar. Operating the radar at two frequencies allows the radar to look at regions spaced at two different distances from the front of the vehicle. Highway related information may be encoded in the frequency selective surface by variations in the shape or dimensions of the frequency selective stripe morphology in order to modulate the reflected signal with highway information which is then also detected at the radar receiver.

Abstract: A weapon transport device transports along a path toward a target in hostile territory, (1) a target-intended weapon and (2) biological, chemical and/or radioactive agents for attacking the occupants of such territory should they execute countermeasures against the weapon transport device. Separation of the biological, chemical and/or radioactive agents is initiated or, where appropriate, inhibited, by signals from either the guidance system of the transport device or from on-board Global Positioning System (GPS) receivers when the transport device strays by more than a predetermined distance from the path, the sensor is blinded, or the transport device passes beyond a predetermined point while en route to the target.

Abstract: The present invention relates to a homing head mounted on a flying body, and intended to guide the flying body towards a target. According to the invention, the homing head includes a target detection system (SD1) comprising a system (SI1) for identifying luminous flashes originating from the target, and a target locating system (SL1), which includes a photosensitive detector (D1) mounted fixedly on the flying body and comprising a matrix of photosensitive sensors, and a means of focussing (6) which projects onto said matrix of the photosensitive detector (D1) the image of the scene situated fore of the flying body.

Abstract: A fully reclinable pivotable airplane premium passenger seat. The seat can be translated and/or pivoted from a daytime position to a nighttime position. In the nighttime position, the seat can be fully extended into unused aisle space. In its fully extended position, the seat back may be placed in a horizontal mode and the leg rest fully extended to permit more restful sleep for passengers in a horizontal position.

Abstract: A feedback motion compensation (FMC) component for use in a spacecraft having a payload. The FMC component includes a controller having sensor data inputs and an open loop dynamics model that is driven by actuator commands to produce a high accuracy attitude estimate suitable for payload motion compensation.

Abstract: The invention relates to an electrical distribution system for energizing a plurality of electric circuits in accordance with a predetermined delay pattern. The system as described comprises a control unit, a plurality of circuit delay arrangements each associated with an electrical circuit individual thereto and each circuit delay arrangement is identifiable by a circuit code individual thereto and includes a pulse counting arrangement. The control unit is arranged to transmit the circuit codes to the circuit delay arrangements and the pulse count individual to each circuit code, and each circuit delay arrangement identified by its circuit code is arranged to store the pulse count individual to that code. On receipt of a start signal from the control unit, transmitted simultaneously to all the circuit delay arrangements, each circuit delay arrangement starts its respective pulse counting arrangement and energizes its respective electrical circuit when the pulse count is completed.

Abstract: A rocket launching system employing ignition apparatus that is used with a small rocket to launch the rocket from a gun. The rocket is equipped with acoustic (pressure) and optical (thermal) sensors that detect a pressure pulse and light flash of a primer charge used to fire the gun. The simultaneous detection of the pressure pulse and the light flash by the sensors generates output signals that are used to complete an electrical circuit in an electronic ignition circuit that activates an igniter that ignites a rocket motor.

Abstract: A pistol with a frame, a barrel and a firing mechanism. The firing mechanism includes a pivotably mounted hammer having a first hammer member and a second hammer member stationarily interlocked in a pocket of the first hammer member. The firing mechanism also includes a trigger assembly with a trigger member and a spacer pivotably mounted to the frame in a slot of the frame. The barrel has a lug on its bottom rear end that is movably mounted to the frame by a lug pin. A rear end of the lug has a contoured shape to accommodate the top of the trigger and a front of a pull bar being moved under the barrel. A handgrip panel is mounted to a handgrip section of the frame by a single fastener. The panel and handgrip section have cooperating angled surfaces to also mount the panel to the frame.

Abstract: A separation system for separating a first section from a second section is disclosed. In one embodiment, the separation system includes first and second doublers for initially interconnecting the first and second sections, an expandable explosive system contained in a cavity defined by the first and second doublers and first and second sections, and first and second staggered grooves positioned on the first and second doublers, the first and second doublers severable along break planes defined by the first and second staggered grooves to facilitate a substantially collision-free separation and ejection of the first section relative to the second section.

Abstract: An improved apparatus (11) for emitting infrared radiation of a desired wavelength includes a primary surface (.[.35.]. .Iadd.25.Iaddend.); a burner (24) for raising the temperature of the primary surface so as to cause the primary surface to emit infrared radiation of a first wavelength; a secondary surface (26) surrounding the primary surface in spaced relation thereto and arranged to be heated by infrared radiation emitted by the first surface and for emitting infrared radiation of a second wavelength toward the object; and an actuator (28) for selectively varying the spacing between the primary and secondary surfaces so that infrared radiation emitted by the secondary surface .[.will be at a desired wavelength and.]. will be focused; whereby the apparatus will emit infrared radiation of a desired wavelength toward the object.